When a satellite is used to perform an Earth observation mission, orbital maneuvers are important when the moving target exceeds the maximum coverage field of the satellite-lite. Fast response observation is achieved by a noncoplanar orbital maneuver. First, the minimum geocentric angle distance between the satellite point trajectory and the target point trajectory is determined via the two-body model, and the time required for the maneuvering satellite to fly over the target point is analytically obtained. On the premise of not changing the shape of the satellite orbit plane, the fastest arrival time of orbit transfer to the target is obtained. Under the condition of satisfying the maximum impulse constraint, the initial satellite orbit change time and the required velocity increments are calculated by the objective function of the minimum fuel consumption and the fastest arrival time. According to the observation of satellites maneuvering to multiple targets, the minimum impulse of satellites maneuvering to the target is obtained. The target allocation of satellites that need to maneuver to each target is performed by using zero-one integer programming. Then, the problem is transformed into an optimization of multiple satellites to single-target maneuvering, and the optimal maneuvering satellites and the required impulse of each target point are obtained.
Fast Orbit Maneuvering Optimization for Network Satellite Observations of Ground Targets
2024-03-22
2728544 byte
Conference paper
Electronic Resource
English
Change of satellite orbit plane by aerodynamic maneuvering
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